Space and Exploration Technology

Matteo Ceriotti, Colin McInnes, Kevin Worrall

Our project objectives

Once in space, spacecraft require efficient orbit and attitude control, to reach new vantage points and orbits, and deliver mission objectives.

Our project methodology

We exploit natural dynamics and develop modern techniques to design orbits, transfers, and control algorithms for future spacecraft missions.
We explore the dynamics of multi-body gravitational interactions and non-gravitational perturbations in order to design new families of efficient spacecraft trajectories. This includes work on new methodologies for trajectory optimisation and the use of light pressure for solar sailing to deliver new families of highly non-Keplerian orbits which can enable entirely new vantage points in space. Applications include the design and control of asteroid proximity orbits using a solar sail. Through new insights into asteroid orbital dynamics we are leveraging multi-body gravitational interactions to reduce the scale of engineering required for asteroid capture. This includes the use of stable invariant manifolds, aerocapture and kinetic impacts. Other work is investigating energy-efficient asteroid dis-assembly using the ‘orbital siphon’ effect and the interaction of economic models with trajectory optimisation and mission design.

We exploit Deep Learning and Artificial Neural Networks to quickly identify feasible and low-cost trajectories to multiple targets, for example asteroids for science or other spacecraft for in-orbit servicing and debris removal. We also use Machine Learning to design new, robust control schemes that can deliver high level of autonomy to complex uncrewed missions, for control of spacecraft attitude, robotic manipulators and flexible appendages and structures, for in-orbit assembly, inspection, or docking.

Our project achievements

Here are a few visualisations of our results:

Reorientation of a large, flexible space structure using a combination of reaction wheels and reflectivity control devices to minimise deformation (yellow line represents the sun direction). Credit: Dr Robbie Gordon

Optimisation of Earth-Moon transfer trajectory (yellow) exploiting invariant manifolds (red) leading to vertical Lyapunov figure-of-eight orbit (blue) around Lagrangian point L1. Credit: Dr Matteo Ceriotti